TURBOFAN ENGINE

• US 20090304518A1
• Filed: 04/06/2007
• Published: 12/10/2009
• Est. Priority Date: 07/04/2006
• Status: Active Grant

• Current Assignee: IHI Corporation
• Original Assignee: IHI Corporation
• Inventors: Goto, Shinya, Murooka, Takeshi, Mizuta, Ikuhisa, Kodama, Hidekazu
• Granted Patent: US 8,579,592 B2
• Time in Patent Office: Days
• US Class Current: 416/223.R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

Claims

1. A turbofan engine comprising:

a fan first-stage rotating blade which takes an air thereinto and has a hub-side leading edge part more extending in a forward direction of the engine than a tip-side leading edge part and a mid-span leading edge part.

2. The turbofan engine according to claim 1, wherein the hub side of the fan first-stage rotating blade is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span.

3. The turbofan engine according to claim 1, wherein a radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

4. The turbofan engine according to claim 1, wherein the leading edge parts are formed toward a downstream side of the engine from the hub side to an outer-diameter side while having a short chord length so as to be smoothly connected to each other in a general fan blade shape at a radial position in a span of 5 to 50% of a trailing edge part.

5. The turbofan engine according to claim 1, wherein the hub-side leading edge part is formed into a substantially linear basic shape or is formed into a convex shape or a concave shape in an outer-radial direction.

6. The turbofan engine according to claim 1, wherein the fan first-stage rotating blade is formed into a shape in which two or a plurality of blades are integrally connected as one with each other by a chemical process or a structural process.